CN109533296A - A kind of connection structure of fuselage and undercarriage rocker arm - Google Patents
A kind of connection structure of fuselage and undercarriage rocker arm Download PDFInfo
- Publication number
- CN109533296A CN109533296A CN201811333192.2A CN201811333192A CN109533296A CN 109533296 A CN109533296 A CN 109533296A CN 201811333192 A CN201811333192 A CN 201811333192A CN 109533296 A CN109533296 A CN 109533296A
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- CN
- China
- Prior art keywords
- connection structure
- bolt
- structure according
- auricle
- oiling channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Connection Of Plates (AREA)
Abstract
The application belongs to technical field of aircraft structure design, in particular to a kind of connection structure of the fuselage of integrated lubrication function and undercarriage rocker arm, the connection structure, comprising: auricle offers oiling channel thereon, and the one end in oiling channel is connected to the through-hole on auricle；Bolt is arranged in through-holes, and can be around own axis；Pressure pump nozzle is connected to the other end in oiling channel.Using the structure as the connection structure of fuselage and undercarriage rocker arm, auricle is connect with fuselage, it is connect at the top of bolt with undercarriage rocker arm, lubricant can be easily infused into through-hole by pressure pump nozzle when the connection structure fills lubricant, realize the lubrication between bolt and auricle, simply, easy to operate, it is not necessary to which that bolt and auricle are dismounted.
Description
Technical field
The application belongs to technical field of aircraft structure design, in particular to the connection knot of a kind of fuselage and undercarriage rocker arm
Structure.
Background technique
The connection structure of fuselage and undercarriage rocker arm passes through for bolt and connects after being fixed on the auricle of fuselage with undercarriage rocker arm
It connects, bolt relatively rotates with auricle during aircraft takeoffs and landings, to reduce abrasion between bolt and auricle and thus producing
Raw corrosion often applies lubricant lubrication therebetween.
Under normal circumstances, lubricant can generate loss in undercarriage use process, to guarantee it to bolt and auricle
Lubricant effect needs just to increase Tu Yici lubricant at regular intervals.Currently, increase lubricant between bolt and auricle, need
Bolt is disassembled from auricle first, then lubricant is coated on bolt or auricle, bolt assembly is gone back thereafter, is restored
The connection relationship of bolt and auricle, since the process also relates to other dismounting for having with the connection structure connection relationship component,
The especially dismounting of bolt and undercarriage rocker arm, the course of work is extremely cumbersome, complicated, expends a large amount of labor and time, work
It is inefficient, and continually bolt and auricle are dismounted, inevitably have an adverse effect to its service life, causing cannot
The preferable working service requirement met to undercarriage.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
The purpose of the application there is provided the connection structure of a kind of fuselage and undercarriage rocker arm, with overcome or alleviated by it is above-mentioned extremely
The problem of few one side.
The technical solution of the application is: a kind of connection structure of fuselage and undercarriage rocker arm, comprising:
Auricle, offers oiling channel thereon, and the one end in oiling channel is connected to the through-hole on auricle；
Bolt is arranged in through-holes, and can be around own axis；
Pressure pump nozzle is connected to the other end in oiling channel.
Preferably, bolt circumferentially offers first and stays oil groove, and first stays oil groove is connected to oiling channel.
Preferably, bolt is provided in the axial direction with the first circulation groove, and the first circulation groove is stayed oil groove with first and is connected to.
Preferably, the first circulation groove has a plurality of, and is circumferentially uniformly distributed along bolt.
Preferably, through-hole wall circumferentially offers second and stays oil groove, and second stays oil groove is connected to oiling channel.
Preferably, through-hole wall is provided in the axial direction with the one or more the second circulation grooves, and the second circulation groove and second stay oil
Slot connection.
Preferably, the second circulation groove has a plurality of, and is uniformly distributed circumferentially.
Preferably, pressure pump nozzle is connect with oiling channel by being threadedly engaged, and in pressure pump nozzle and oiling channel
Steel-wire screw-socket is provided between logical.
Preferably, above-mentioned connection structure further includes having: two bushings, is arranged between through-hole wall and bolt；Two bushing phases
Pair end face between have gap, gap is connected to oiling channel.
Preferably, bushing is provided in the axial direction with third circulation groove, third circulation groove and gap area close to the wall surface of bolt.
Preferably, third circulation groove has a plurality of, and is uniformly distributed circumferentially.
At least there are following advantageous effects in the application: a kind of connection structure of fuselage and undercarriage rocker arm, and the knot is enough
It is provided with pressure pump nozzle, pressure pump nozzle is connected to by oiling channel with the through-hole on auricle.Using the structure as fuselage with
Auricle is connect by the connection structure of undercarriage rocker arm with fuselage, is connect at the top of bolt with undercarriage rocker arm, can be passed through pressure as a result,
Power pump nozzle easily infuses lubricant into through-hole, realizes the lubrication between bolt and auricle, simple, easy to operate, it is not necessary to bolt
It is dismounted with auricle.
Detailed description of the invention
Fig. 1 is the structural representation of the fuselage of the application integrated lubrication function Yu one embodiment of connection structure of undercarriage rocker arm
Figure；
Fig. 2 is the explosive view of the application embodiment illustrated in fig. 1；
Fig. 3 is the sectional view along A-A in Fig. 1.
Wherein:
1- auricle；2- pressure pump nozzle；3- bushing；4- bolt；5- steel-wire screw-socket.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 3 the application is described in further details with reference to the accompanying drawing.
A kind of connection structure of fuselage and undercarriage rocker arm, comprising:
Auricle 1, offers oiling channel thereon, and the one end in oiling channel is connected to the through-hole on auricle 1；
Bolt 4 is arranged in through-holes, and can be around own axis；
Pressure pump nozzle 2 is connected to the other end in oiling channel.
Further, the connection structure of above-mentioned fuselage and undercarriage rocker arm, bolt 4 circumferentially offer first and stay oil groove,
First stays oil groove is connected to oiling channel；Bolt 4 is provided in the axial direction with the first circulation groove, the first circulation groove and the first company in oil groove
It is logical；First circulation groove has a plurality of, and is uniformly distributed circumferentially.In the present embodiment, oil groove is stayed in setting first, wherein profit can be stored
Lubrication prescription extends filling lubricant maintenance interval, avoids continually filling lubricant, while being arranged a plurality of equally distributed first-class
Through slot can make lubricant be evenly distributed, and improve lubricant effect.
Further, the connection structure of above-mentioned fuselage and undercarriage rocker arm, through-hole wall circumferentially offer second and stay oil
Slot, second stays oil groove is connected to oiling channel.Through-hole wall is provided in the axial direction with the one or more the second circulation grooves, the second circulation
Slot is stayed oil groove with second and is connected to；Second circulation groove has a plurality of, and is uniformly distributed circumferentially.Oil groove is stayed in setting second, wherein can store
Lubricant is hidden, extends filling lubricant maintenance interval, avoids continually filling lubricant, while being arranged a plurality of equally distributed the
Two circulation grooves can make lubricant be evenly distributed, and improve lubricant effect.
Further, the connection structure of above-mentioned fuselage and undercarriage rocker arm, pressure pump nozzle 2 and oiling channel pass through screw thread
It is cooperatively connected, and is provided with steel-wire screw-socket 5 between pressure pump nozzle 2 and oiling channel are logical, in pressure pump nozzle 2 and oiling
Elastic connection is formed between channel is logical, eliminates screw thread foozle, improves bonding strength.
Further, the connection structure of above-mentioned fuselage and undercarriage rocker arm further includes having: two bushings 3, is arranged in through-hole
Between wall and bolt 4；There is gap, gap is connected to oiling channel between the opposite end face of two bushings 3；Bushing 3 is close to bolt 4
Wall surface be provided in the axial direction with third circulation groove, third circulation groove and gap area；Third circulation groove has a plurality of and circumferentially equal
Even distribution.The friction between bolt 4 and auricle 1 two bushings 3 are set on the one hand can be reduced, the direct mill between bolt 4 and auricle 1 is reduced
Damage；On the other hand there are gaps between two bushings 3, can be used as the storage space of lubricant, extend filling lubricant maintenance interval,
It avoids continually filling lubricant；Lubricant distribution can be made equal in addition, a plurality of equally distributed third circulation groove is arranged in bushing 3
It is even, improve lubricant effect.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. the connection structure of a kind of fuselage and undercarriage rocker arm characterized by comprising
Auricle (1), offers oiling channel thereon, and the one end in the oiling channel is connected to the through-hole on the auricle (1)；
Bolt (4) is arranged in the through hole, and can be around own axis；
Pressure pump nozzle (2) is connected to the other end in the oiling channel.
2. connection structure according to claim 1, which is characterized in that the bolt (4) circumferentially offers first and stays oil
Slot, described first stays oil groove is connected to the oiling channel.
3. connection structure according to claim 2, which is characterized in that the bolt (4) is provided in the axial direction with the first circulation
Slot, first circulation groove are stayed oil groove with described first and are connected to.
4. connection structure according to claim 3, which is characterized in that first circulation groove have it is a plurality of, and along around described
The circumferential direction of bolt (4) is uniformly distributed.
5. connection structure according to claim 1, which is characterized in that the through-hole wall circumferentially offers second and stays oil
Slot, described second stays oil groove is connected to the oiling channel.
6. connection structure according to claim 5, which is characterized in that the through-hole wall is provided in the axial direction with one or more
The second circulation groove of item, second circulation groove are stayed oil groove with described second and are connected to.
7. connection structure according to claim 6, which is characterized in that second circulation groove has a plurality of and circumferentially equal
Even distribution.
8. connection structure according to claim 1, which is characterized in that the pressure pump nozzle (2) and the oiling channel
Steel-wire screw-socket (5) are provided with by being threadedly engaged connection, and between the pressure pump nozzle (2) and the oiling channel are logical.
9. connection structure according to claim 1, which is characterized in that further include having: two bushings (3), setting is described logical
Between hole inner wall and the bolt (4)；There is gap, the gap and the note between the opposite end face of two bushings (3)
Oily channel connection.
10. connection structure according to claim 9, which is characterized in that wall of the bushing (3) close to the bolt (4)
Face is provided in the axial direction with third circulation groove, the third circulation groove and the gap area；The third circulation groove have it is a plurality of, and
Circumferential direction along the bolt (4) is uniformly distributed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811333192.2A CN109533296A (en) | 2018-11-09 | 2018-11-09 | A kind of connection structure of fuselage and undercarriage rocker arm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811333192.2A CN109533296A (en) | 2018-11-09 | 2018-11-09 | A kind of connection structure of fuselage and undercarriage rocker arm |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109533296A true CN109533296A (en) | 2019-03-29 |
Family
ID=65846593
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811333192.2A Pending CN109533296A (en) | 2018-11-09 | 2018-11-09 | A kind of connection structure of fuselage and undercarriage rocker arm |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109533296A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110397729A (en) * | 2019-08-12 | 2019-11-01 | 合肥华骏汽车部件有限公司 | A kind of Rocker arm assembly of riveting process |
| EP3736065A1 (en) * | 2019-05-10 | 2020-11-11 | Goodrich Corporation | Additively manufactured lubrication channels |
| US11312483B2 (en) | 2019-05-10 | 2022-04-26 | Goodrich Corporation | Landing gear with hydraulic fluid channels |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB696744A (en) * | 1951-04-14 | 1953-09-09 | Thompson Prod Inc | Improvements in or relating to pivot linkage assemblies |
| CN202180849U (en) * | 2011-07-31 | 2012-04-04 | 徐工集团工程机械股份有限公司江苏徐州工程机械研究院 | Mineral dumper steering rocker arm with internally embedded shaft sleeve |
| CN205806115U (en) * | 2016-05-31 | 2016-12-14 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bolt assembly |
| CN207018330U (en) * | 2017-03-30 | 2018-02-16 | 浙江中通汽车零部件有限公司 | A kind of tire bolt |
| CN207375011U (en) * | 2017-09-04 | 2018-05-18 | 彩虹无人机科技有限公司 | A kind of unmanned plane transports special undercarriage buffer unit |
-
2018
- 2018-11-09 CN CN201811333192.2A patent/CN109533296A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB696744A (en) * | 1951-04-14 | 1953-09-09 | Thompson Prod Inc | Improvements in or relating to pivot linkage assemblies |
| CN202180849U (en) * | 2011-07-31 | 2012-04-04 | 徐工集团工程机械股份有限公司江苏徐州工程机械研究院 | Mineral dumper steering rocker arm with internally embedded shaft sleeve |
| CN205806115U (en) * | 2016-05-31 | 2016-12-14 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bolt assembly |
| CN207018330U (en) * | 2017-03-30 | 2018-02-16 | 浙江中通汽车零部件有限公司 | A kind of tire bolt |
| CN207375011U (en) * | 2017-09-04 | 2018-05-18 | 彩虹无人机科技有限公司 | A kind of unmanned plane transports special undercarriage buffer unit |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3736065A1 (en) * | 2019-05-10 | 2020-11-11 | Goodrich Corporation | Additively manufactured lubrication channels |
| US11167865B2 (en) | 2019-05-10 | 2021-11-09 | Goodrich Corporation | Additively manufactured lubrication channels |
| US11312483B2 (en) | 2019-05-10 | 2022-04-26 | Goodrich Corporation | Landing gear with hydraulic fluid channels |
| CN110397729A (en) * | 2019-08-12 | 2019-11-01 | 合肥华骏汽车部件有限公司 | A kind of Rocker arm assembly of riveting process |
| CN110397729B (en) * | 2019-08-12 | 2024-04-30 | 合肥华骏汽车部件有限公司 | Rocker arm assembly of riveting process |
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| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190329 |
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| WD01 | Invention patent application deemed withdrawn after publication |